بررسی تاثیر تعداد حفره بر بازده احتراقی و ضریب بازیافت فشار سکون در محفظه احتراق مافوق صوت

نوع مقاله: مقاله پژوهشی

نویسندگان

1 گروه مهندسی مکانیک، واحد نجف آباد، دانشگاه آزاد اسلامی، نجف آباد، ایران

2 هیات علمی دانشگاه آزاد اسلامی واحد نجف آباد

چکیده

با توجه به این‌که پایداری شعله در موتورهای اسکرم‌جت از چالش‌های اساسی پیش‌روی توسعه‌ی این‌گونه موتورهاست، در مطالعه‌ی حاضر به بررسی عددی تاثیر حفره در محفظه احتراق مافوق صوت یک اسکرم‌جت پرداخته شده است. در این شبیه‌سازی دو بعدی از مدل اغتشاشی k-ɛ استاندارد و مدل احتراقی واکنشگاه نیمه مخلوط (PaSR) استفاده شده است. جریان هوا به‌صورت مافوق صوت و با عدد ماخ 2/05 به محفظه احتراق وارد می‌شود. سوخت هیدروژن نیز در شرایط صوتی و به‌طور متقاطع درون جریان هوا تزریق می‌شود. در این محفظه‌ احتراق، به منظور پایدارسازی شعله از حفره استفاده شده و تاثیر نحوه‌ قرارگیری حفره و تعداد حفره‌ها بر ساختار جریان، بازده احتراقی و ضریب بازیافت فشار سکون مورد مطالعه قرار گرفته است. نتایج حاصل نشان می‌دهد، با افزایش تعداد حفره‌ها از یک تا چهار، بازده احتراقی افزایش یافته اما ضریب بازیافت فشار سکون کاهش می‌یابد. برای پیکربندی با چهار حفره بازده احتراقی برابر 98% و ضریب بازیافت فشار سکون برابر 46/13% است که نسبت به پیکربندی تک‌حفره تقریباً با افزایش 26% بازده احتراقی و کاهش 10% ضریب بازیافت فشار سکون همراه است. بهترین عملکرد در پیکربندی‌های مورد مطالعه مربوط به محفظه احتراق با دو حفره موازی و دو پاشنده سوخت است.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Effect of the number of cavity flame-holders on combustion efficiency and pressure recovery factor in a supersonic combustion chamber

چکیده [English]

In the present research work, computational simulation of the multi cavity scramjet combustor has been performed by using the two-dimensional compressible Reynolds-Averaged Navier Stokes (RANS) equations coupled with two equations standard k-ɛ turbulence model as well as PaSR model for combustion modeling. In this combustion chamber, the supersonic air with Mach number of 2.05 flows in the enclosure, and the transverse hydrogen fuel injection is employed at sonic condition. The cavity is used to stabilize the flame in the combustor and the effect of cavity location and also the number of cavities on flow structure, combustion efficiency, and pressure recovery factor are studied. The results show that by increasing the number of cavities from one to four, the combustion efficiency is increased but the pressure recovery factor decreases. For the four-cavity configuration, the combustion efficiency is around 98% and the pressure recovery factor is 46.13%, which shows 26% increase in the combustion efficiency and 10% decrease in the pressure recovery factor as compared with the single-cavity. In the considered configurations, the best performance is achieved by the parallel dual-cavity with two-injection combustor.

کلیدواژه‌ها [English]

  • Supersonic combustion
  • Scramjet
  • Hydrogen fuel
  • Cavity flame holder
  • Combustion efficiency
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